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  1. StressMan2506

    STRESS CONCENTRATION FACTOR, SHORT CHAMFER IN EDGE OF CIRCULAR APERTURE

    Special thanks to MNLiaison. The linked paper certainly looks pertinent to my case. Thorough study will tell. Regards, StressMan
  2. StressMan2506

    STRESS CONCENTRATION FACTOR, SHORT CHAMFER IN EDGE OF CIRCULAR APERTURE

    Thanks, guys. The blend is at a systems penetration in a wing rib. To design, fatigue life is very high. Treating the blend as a chamfer around the entire circumference and calculating an effective plain hole diameter leads to a stress increase at the attachment holes - no problem. I am left...
  3. StressMan2506

    STRESS CONCENTRATION FACTOR, SHORT CHAMFER IN EDGE OF CIRCULAR APERTURE

    Fellow Stress Engineers: Do any of you know of a reference to a stress concentration factor in-way-of a chamfer over a small proportion of the circumference of a circular aperture; see attached view. Thanks in anticipation...
  4. StressMan2506

    STABILITY OF RECTANGULAR PLATE UNDER EQUAL UNIFORM COMPRESSION ON TWO OPPOSITE EDGES 'b'

    Fellow Stress Engineers: Roark (6th & 7th editions, tables 35 & 15.2 respectively) includes 6 cases covering the above condition, namely:- a) All edges simply supported b) All edges clamped c) Edges b simply supported, edges a clamped d) Edges b simply supported, one edge a simply supported...
  5. StressMan2506

    COMPOSITE LAY-UP NOTATION

    Thanks, SWComposites. The perfect answer; no ambiguity!
  6. StressMan2506

    COMPOSITE LAY-UP NOTATION

    Thanks Compositepro. I interpret your reply as being that, with woven material, the sequence 0/45/90 is never used. Have I got it right? How would you interpret [[(0,90)/(±45)]3]s? Thanks in anticipation.
  7. StressMan2506

    COMPOSITE LAY-UP NOTATION

    Fellow composite-using engineers: Thread327-334726 covered similar ground to my present query. I have a document containing lay-up notation [[(0,90)/(±45)]3]s. I am working with structural analysis in which this lay-up has been interpreted as 0/45/90/-45/0/45/45/0/-45/90/45/0, i.e...
  8. StressMan2506

    BOLT LOADS CALCULATED BY NACA TECH. NOTE 1051

    Hi Nidhish: I've not worked with this stuff since November, so I need to refresh my memory; I'll get back to you... Louis
  9. StressMan2506

    POST-BUCKLING CUT-OFF OF CURVED STIFFENED PANELS (COMPOSITE SKIN & STRINGER)

    They could be, but I'm seeking an independent source to get a handle on what the concept means and how my concession case would affect it...
  10. StressMan2506

    POST-BUCKLING CUT-OFF OF CURVED STIFFENED PANELS (COMPOSITE SKIN & STRINGER)

    Thanks, rb1957. "Composite" here means "plastic" skin & stringer. A note in one of our output files suggests that the "post-buckling cut-off" parameter is a limit applied to the loading to prevent debonding of stringer from skin. It appears in "incomplete diagonal tension" analysis and is...
  11. StressMan2506

    POST-BUCKLING CUT-OFF OF CURVED STIFFENED PANELS (COMPOSITE SKIN & STRINGER)

    Fellow Stress Engineers: Do any of you have any references to post-buckling cut-off as applied to the above structural form? I've taken a look at the manual for the software we're using, but, as expected, it doesn't really enlighten me. I need to use engineering judgement on a low concession...
  12. StressMan2506

    BI-METALLIC MEMBER SUBJECT TO END LOAD & BENDING MOMENT

    Thanks, guys.
  13. StressMan2506

    BI-METALLIC MEMBER SUBJECT TO END LOAD & BENDING MOMENT

    Fellow Stress Engineers: I am investigating a doubler on one flange of an extruded I-section. The tensile & compressive E values of the I-section are, respectively 1.02 & 1.03 times those of the strap. I have some familiarity with calculating such sections under end load or bending moment, but...
  14. StressMan2506

    BUCKLING OF A TAPERED PLATE

    Thank you very much!
  15. StressMan2506

    BOLT LOADS CALCULATED BY NACA TECH. NOTE 1051

    Thanks, guys. GrandpaDave: The thread you provided the link for refers to TN 1458 as a follow-up to TN 1051. Huth quotes 1051 as a reference, but not 1458; I'll check it out. rb1957: I did mean equation 1 of TN 1051. 'C' therein is bolt flexibility, which may be calculated by the method...
  16. StressMan2506

    BOLT LOADS CALCULATED BY NACA TECH. NOTE 1051

    Fellow Stress Engineers: Is anyone familiar with this document (PRELIMINARY INVESTIGATION OF THE LOADS CARRIED BY INDIVIDUAL BOLTS IN BOLTED JOINTS)? One would expect that the 1st & last fasteners in a row would be equally loaded, the 2nd & penultimate likewise, and so on, but this is not what...
  17. StressMan2506

    BUCKLING OF A TAPERED PLATE

    Thanks once again, Ed. I studied civil engineering and worked for some years in the offshore oil & gas industry; the term "compact section" rings a bell. I'm close to writing a justification based on numbers and reasoning, but I may have overlooked lateral loading; I need to look further into...
  18. StressMan2506

    BUCKLING OF A TAPERED PLATE

    Thanks, again Ed. A couple of points: I take it that the stepped plate notes are your own work. If so, I would not be able to cite the method in my concession justification. My flange has b/t < 5, so Roark's table doesn't apply. Assuming a uniform flange of thickness = post-blend minimum...
  19. StressMan2506

    BUCKLING OF A TAPERED PLATE

    Hi edbgtr: I've taken a look at your attachment. With reference to Roark, 7th edn, Table 15.2, case 1d, it appears that the work was based upon a long,narrow plate. The following statement appears at the top of Roark's table: "...the smaller width should be greater than 10 times the thickness...
  20. StressMan2506

    BUCKLING OF A TAPERED PLATE

    Thanks, guys. You're right, rb1957, I did consider min. & mean and I agree that blending out a tool mark generally affects a small length, but, in this case, the blend was not as well executed as it could have been. If the thin run had passed, the job would have been done. The mean run left me...

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